DLR-F6翼身组合体跨音速流场CFD应用计算研究  

CFD Calculation Application Research of Transonic Flow Field Around DLR—F6 Wing Body Configuration

作　　者：高飞飞[1] 李中武[1] 曹平宽[1] 梁益华[1] 

机构地区：[1]西安航空计算技术研究所,气动数值模拟航空科技重点实验室,西安710068

出　　处：《科学技术与工程》2011年第17期4011-4017,共7页Science Technology and Engineering

基　　金：航空科学基金项目(20091431003)资助

摘　　要：针对跨音速运输机经典算例DLR—F6翼身组合体模型,采用CFD方法对其气动特性进行了黏性流动数值模拟,流动模型为雷诺平均N-S(RANS)方程。首先采用"超立方体"概念生成绕DLR—F6翼身组合体的高质量多块结构拼接网格,研究网格拓扑结构对气动特性的影响。在此基础上通过网格细分和粗分考查了网格密度对计算结果的影响,最后进行了湍流模型的影响研究。通过与实验数据对比分析,得出了适宜DLR—F6翼身组合体跨音速黏性流动的计算网格,并总结出了能较好模拟其跨音速流场特性的湍流模型。结果表明:网格拓扑结构的合理设计会对计算结果产生一定的影响。网格密度对机翼表面压力分布没有明显影响,但对阻力系数影响显著。湍流模型对机翼表面压力系数分布的影响主要体现在激波位置上,对翼根处的分离也有一定的影响。SST模型计算的气动力系数比SA模型接近实验值。In the case of DLR—F6 wing body configuration model,which is the classical calculation of transonic transporter,applied CFD methods to carry on numerical simulation of viscous flow about its aerodynamic characteristics. Flow model was Navier-Stokes（RANS） equations.To start with,＂Tesseract hypercube＂conception is applied to generate high quality multi-block patching grid.And then the influence of grid topology structure on the aerodynamic characteristics of DLR—F6 wing body configuration is studied,based on which examined the influence of grid density on the calculation results using grid refinement/unrefinement method.In the end,a study of the influence of turbulence model is made.Through the contrastive analysis of the experiment data,the suitable calculation grid for transonic viscous flow around DLR—F6 wing body configuration is obtained,and summarized turbulence models which simulated its aerodynamic characteristics more appropriately.The results show that grid topology exerts certain effects on the computational results.The pressure coefficient distribution is slightly affected by the grid density.The turbulence models exert some effects on the pressure distribution,especially on the position of shock wave and obvious effects on the root of wing.The Menter k-omega SST model achieves the higher accuracy than the Spalart Allmaras model.

关 键 词：翼身组合体 RANS方程 湍流模型 计算网格 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]